JP2019167957A - Tip shroud fillets for turbine rotor blades - Google Patents

Abstract

To provide a turbine rotor blade including an airfoil, a tip shroud, and a fillet formed therebetween.SOLUTION: A fillet 50 defines a fillet profile variable about an intersection for connecting a tip shroud 48 and an airfoil 46 and facilitating an aerodynamic airflow. The fillet 50 includes a pressure side fillet. The pressure side fillet comprises a pressure side fillet profile per point within a first set of points of X, Y and Z coordinate values in a Cartesian coordinate system, where X, Y and Z are distances in inches from an origin and, when the points are connected by smooth continuing arcs, the points define the pressure side fillet profile of the pressure side fillet. The first set of points includes points included between a point 1 and a point 50 of each reference plane included between a reference plane H and a reference plane W.SELECTED DRAWING: Figure 4

Description

  The present invention relates generally to fillets for use with turbine rotor blades, and more particularly to fillets for use between turbine rotor blade airfoils and tip shrouds.

  At least some known turbine rotor blades include an airfoil, a platform, a shank, a dovetail extending along a radially inner end of the shank, and a tip shroud formed at the tip of the airfoil. . In at least some known airfoils, an integral tip shroud is included at the radially outer end of the airfoil to define the portion of the passage through which hot combustion gases must pass. Known tip shrouds and airfoils typically include a fillet having a predetermined size and shape at the intersection of the tip shroud and the airfoil.

  In operation, the connection formed between the tip shroud and the airfoil of such a rotor blade becomes very stressed due to centrifugal and mechanical forces caused by the rotation. The fillet formed between the tip shroud and the airfoil is shaped to reduce the stress concentration that occurs in this region. However, known fillet shapes still allow the construction of stress concentrations that reduce the useful life of the component. In addition, known fillets can reduce engine efficiency due to drag and blockage caused by the fillets. Therefore, there is a need for an improved fillet shape that further reduces stress concentration while also being aerodynamically implemented to promote engine efficiency.

US Patent Application Publication No. 2017/0226870

  Accordingly, the present application describes a rotor blade for a turbine of a gas turbine that includes an airfoil, a tip shroud, and a fillet formed around the intersection of the airfoil and the tip shroud. The fillet defines a variable fillet profile around the intersection to connect the tip shroud and the airfoil and promote aerodynamic airflow. The fillet includes a pressure surface fillet formed between the pressure surface of the airfoil and the inner surface of the tip shroud, and a suction surface fillet formed between the suction surface of the airfoil and the inner surface of the tip shroud. . The pressure surface fillet includes a pressure surface fillet profile that substantially coincides with a point in the first set of X, Y, Z coordinate values in the Cartesian coordinate system, as shown in Table I, where X, Y, Z are distances from the origin in inches, and when the points in the first set of points are connected by a smooth continuous arc, the points in the first set of points are pressure surfaces Define the pressure face fillet profile of the fillet. The first set of points includes each point included between point 1 and point 50 of each reference surface included between reference surface H and reference surface W, as shown in Table I.

  The present application further describes a rotor blade for a turbine of a gas turbine that includes an airfoil, a tip shroud, and a fillet formed around the intersection of the airfoil and the tip shroud. The fillet defines a variable fillet profile around the intersection to connect the tip shroud and the airfoil and promote aerodynamic airflow. The fillet includes a pressure surface fillet formed between the pressure surface of the airfoil and the inner surface of the tip shroud, and a suction surface fillet formed between the suction surface of the airfoil and the inner surface of the tip shroud. . The suction side fillet includes a suction side fillet profile that substantially coincides with a point in the first set of points of the X, Y, Z coordinate values in the Cartesian coordinate system, as shown in Table II, where X, Y, and Z are distances from the origin in inches. When the points in the first set of points are connected by a smooth continuous arc, the points in the first set of points are suction surfaces Define the suction side fillet profile of the fillet. The first set of points includes each point included between point 1 and point 50 of each reference surface included between reference surface H and reference surface W, as shown in Table I.

  These and other features of the present invention will be more fully understood and appreciated by careful consideration of the following more detailed description of exemplary embodiments of the invention in conjunction with the following accompanying drawings. Let's be done.

1 is a schematic diagram of an exemplary gas turbine engine. FIG. 1 is a schematic diagram of an exemplary hot gas path that may be defined through a gas turbine engine. FIG. 1 is a perspective view of an exemplary tip shrouded turbine rotor blade according to an embodiment of the present invention. FIG. 1 is a perspective view of an exemplary pressure side fillet according to an embodiment of the present invention. FIG. 1 is a perspective view of an exemplary suction side fillet according to an embodiment of the present invention. FIG. FIG. 6 is a radially outer cross-sectional view of an airfoil profile cross section taken along line 6-6 of FIG. 3 showing pressure and suction face fillets according to an embodiment of the present invention. FIG. 3 is a perspective view of a tip shroud airfoil showing the X, Y, Z coordinate system used herein, illustrating a fillet profile by defining a number of discrete points occurring therein. . It is a schematic sectional drawing of the airfoil part which shows the reference plane relevant to the X, Y, Z coordinate system of FIG. FIG. 9 is a cross-sectional view of a fillet along an exemplary one of the reference planes shown in FIG.

  A tip shroud including a fillet may be integrally formed with the turbine rotor blade at the radially outer end of the airfoil. The tip shroud generally provides a surface area that covers the tip of the airfoil. In operation, the tip shroud engages the tip shroud of circumferentially adjacent rotor blades at both ends, thereby forming a generally annular ring or shroud that substantially surrounds the hot gas path. This annular ring includes expansion combustion to improve engine efficiency. The fillet joins the tip shroud to the airfoil, thereby supporting the tip shroud to prevent the tip shroud from detaching from the airfoil during operation.

  In general, from the standpoint of engine performance, it is desirable to have a relatively large tip shroud that overhangs both the pressure and suction surfaces of the outer radial tip of the airfoil. However, with regard to aerodynamic performance, it is advantageous for the tip shroud fillet to remain as small and streamlined as possible. While these competing benefits, the tip shroud is large enough to divert the maximum amount of working fluid possible beyond the airfoil, the fillet is small to promote aerodynamic efficiency. And given that it remains streamlined, it should be understood that the design of the tip shrouds and the fillets that support them is a rigorous and highly specialized task. A successful design effectively balances the high stresses created on both sides of the airfoil by the mass of the overhanging tip shroud, thereby significantly extending component life and allowing for a larger tip shroud. And / or the fillet size can be reduced to improve aerodynamic performance. As will be appreciated, the present application discloses a fillet design that is specifically adapted to achieve these objectives. That is, the fillets of the present disclosure, also referred to herein as “the present invention” or “the present fillets,” reduce the mass of the fillet region so that the fillets remain streamlined for aerodynamic performance. While still providing a structural configuration that further reduces stress concentrations and supports larger tip shrouds without sacrificing lifetime.

  By way of background, FIG. 1 is a schematic diagram of an exemplary gas turbine engine 12 including a compressor 15, a combustor 16, and a turbine 22 extending therethrough from an intake side to an exhaust side, all coupled in a series flow configuration. Has been. The engine 12 includes a central axis 23 and a hot gas path is defined from the intake side to the exhaust side. During operation, air flows into the intake side and is sent to the compressor 15. The compressed air is directed from the compressor 15 to the combustor 16 where it is mixed with fuel and ignited to produce combustion gases. Combustion gas is directed through the hot gas path from the combustor 16 to the turbine 22, which converts the thermal energy into mechanical energy to compress 15 and / or a generator (not shown), etc. To power another load.

  FIG. 2 is a schematic diagram of an exemplary hot gas path 20 defined in multiple stages of a turbine 22 used in gas turbine engine 12. Three stages are shown, each stage including a row of vanes or nozzles 24 and a row of buckets or rotor blades 26. Each row of nozzles 24 includes a plurality of nozzles 24 circumferentially spaced about an axis 23 (shown in FIG. 1). Each row of rotor blades 26 includes a plurality of rotor blades 26 spaced circumferentially around a rotor disk 27 so as to rotate about an axis 23. It should be understood that the nozzle 24 and the rotor blade 26 are each disposed in the hot gas path 20 of the turbine 22. The direction of gas flow through the hot gas path 20 is indicated by arrows 36.

  FIG. 3 shows a perspective view of a rotor blade 26 according to an exemplary embodiment of the present invention. As shown, the rotor blade 26 may include a platform 40, a shank 42, a dovetail 44, a tip shroud 48, and a fillet 50. Dovetail 44 is used to couple rotor blade 26 to rotor disk 27 (as shown in FIG. 2). The rotor blade 26 may also include an airfoil 46 that extends radially between the platform 40 and the tip shroud 48. The airfoil 46 has a leading edge 52, a trailing edge 54, a pressure surface 53, and an opposite suction surface 55. The pressure surface 53 extends from the leading edge 52 to the trailing edge 54 and forms a concave outer surface of the airfoil 46. The suction surface 55 extends from the leading edge 52 to the trailing edge 54 and forms the convex outer surface of the airfoil 46. A fillet 50 is defined and extends between the airfoil 46 and the tip shroud 48. More specifically, the fillet 50 extends into an intersection formed between the outer radial tip 49 of the airfoil 46 and the tip shroud 48, thereby structurally supporting the tip shroud 48. The tip shroud 48 may include circumferentially extending seal rails 56 and cutter teeth 57 that facilitate sealing with a stationary casing. During operation, hot combustion gases flow across both the pressure surface 53 and the suction surface 55 of the airfoil 46 and cause the rotor blades 26 to rotate. Specifically, the flow of hot gas on the pressure surface 53 and suction surface 55 of the airfoil 46 causes the rotor blades 26 to rotate on each rotor disk 27 so that the energy of the expanding hot gas is mechanical. Converted into energy.

  As shown in FIG. 3, the airfoil 46 includes an airfoil height 61 that represents the overall height of the airfoil 46 (ie, the distance between the platform 40 and the tip shroud 48), and the entire airfoil 46. And an airfoil width 62 representing the width (ie, the distance between the leading edge 52 and the trailing edge 54). As described below, one method of defining the fillet 50 is to define a widthwise portion or range within the airfoil width 62, for each of which the height of the fillet 50 (or of the fillet 50). Defining a range of heights within which the height is maintained. As used herein, the height of the fillet 50 represents the radial distance that the fillet 50 extends from the outermost tip of the airfoil 46 toward the platform 40. For purposes described herein, the outermost tip of the airfoil 46 is considered to be coplanar with the radially inner surface 60 of the tip shroud 48. (As shown in FIGS. 4 and 5, the inner surface 60 of the tip shroud 48 is opposite the outer surface 64.) Further, for purposes of illustration, the height of the fillet 50 is herein referred to as an airfoil. For example, it can be expressed as a percentage of the airfoil height 61 with respect to the total height of the portion 46.

  Referring now to FIGS. 4-6, a more detailed view of the fillet 50 is provided. (Note that FIGS. 4-9 are not drawn to scale and are provided only to illustrate the methodology for locating specific points, and the actual positions of those points are shown in Tables I and II. Therefore, if there is a discrepancy between the apparent point location shown in the drawing and the actual location listed in Table I and Table II, in all cases, It should be understood that the location of the points provided in Tables I and II is dominant and decisive, especially with reference to points made within the scope of the appended claims.) FIG. FIG. 5 shows a perspective view of the fillet 50 on the pressure surface 53 of the airfoil 46. The fillet 50 on the pressure surface 53 can be more specifically referred to herein as a “pressure surface fillet 63”. FIG. 5 shows a perspective view of the fillet 50 on the suction surface 55 of the airfoil 46. The fillet 50 on the suction surface 55 can be more specifically referred to herein as the “suction surface fillet 65”. The outer edge of the fillet 50 is formed at the intersection between the fillet 50 and the airfoil 46 at both the pressure surface 53 and the suction surface 55 and is indicated by the intersection line 58. The outer edge of the fillet 50 is also formed at the intersection between the fillet 50 and the tip shroud 48 and is indicated by the intersection line 59. Intersection line 59 is most clearly shown in FIG. 6, which provides a cross-sectional view of a portion of airfoil 46 and fillet 50 taken along line 6-6 of FIG. Also shown in FIGS. 4-6 are some additional reference lines 71 as well as points specifically located on those reference lines 71 that can be used to define the profile of the fillet 50. As discussed further with respect to FIGS. 7-9, reference lines 71 each represent the intersection of a reference surface (eg, reference surfaces A to Z) and the surfaces of pressure surface fillet 63 and suction surface fillet 65.

  In accordance with the present invention, as can be seen, the fillet 50 is configured to extend over most of the inner surface 60 of the tip shroud 48, as indicated by the cross line 59. Fillet 50 is also configured to enclose and cover tip 49 of airfoil 46, as indicated by cross line 58. Further, between the intersecting line 58 and the intersecting line 59, the fillet 50 of the present invention has a thickness that varies to form a specific surface contour, configuration, or profile that improves aerodynamic and structural performance. Have. As will be appreciated, the exact configuration of the fillet 50 is optimal, with some competing design criteria, and the complex relationships that exist between them, taken into account and balanced to result in optimized performance. Based on Repeated tests have shown that the fillet 50 of the present invention is superior to other known fillet configurations, particularly when combined with a tip shroud having a specific profile. For example, while the configuration of the present fillet 50 is streamlined with respect to aerodynamic performance, the tip shroud 48 is structurally configured to optimally distribute and balance operating stresses to substantially extend the useful life of the rotor blades. I also support.

  Referring now to FIGS. 7-9, an X, Y, Z coordinate system is shown, which is used to define a particular configuration of the fillet 50, as provided below. It will be. That is, the fillet 50 of the present invention is described by defining one or more of its surfaces or profiles, which are transmitted via the X, Y, Z coordinate system shown in FIGS. This is explained by defining several discrete points that occur in them. As can be seen, in FIG. 7, the general orientation of the X, Y, Z coordinate system is shown with respect to the rotor blade 26. As shown, the Z axis is oriented along the chord of the airfoil 46 of the rotor blade 26. Thus, the Z-axis extends horizontally between the intersection of the leading edge 52 and trailing edge 54 of the airfoil 46. With respect to the Y axis, it extends perpendicular to the longitudinal direction of the airfoil 46. Finally, as shown, the X axis extends perpendicular to both the Y and Z axes. The X axis, the Y axis, and the Z axis intersect at the origin 72.

  Exemplary points occurring on the surface or profile of the fillet 50 (including both pressure side fillet 63 and suction side fillet 65) are X, Y, Z coordinates as shown in Tables I and II below. Defined by Exemplary embodiments of the fillet 50 may be substantially all of the fillet profile of the illustrated fillet 50, as can be illustrated by all the points contained in Tables I and II; or One or both of the pressure and suction surfaces of the fillet 50 may include a specific surface area or profile defined within the illustrated fillet 50, as may be defined by a set of points representing a subset of included points. Please understand that. The points listed in Table I and Table II are in accordance with several cross-section reference planes that intersect the fillet 50 at both the pressure and suction surfaces, i.e., reference surfaces A through Z, as shown most clearly in FIG. Be placed. Table I includes points that occur on the pressure surface of the fillet 50, Table II includes points that occur on the suction surface of the fillet 50, and each table places points relative to the reference surface. Reference planes A to Z are defined between the leading edge 52 and trailing edge 54 of the airfoil 46 at predetermined intervals along the Z axis. Reference planes A to Z are parallel to each other and are oriented perpendicular to the Z axis. Further, Table I and Table II include 100 points on each reference surface, 50 of which occur on the pressure side fillet 63 and 50 on the suction side fillet 65.

  Therefore, as shown most clearly in FIG. 9, at each position on one of the reference planes A to Z on the Z axis, the profile of the fillet of the present invention is the pressure surface of Table I and the suction surface of Table II. Both are defined by points defined by X-axis and Y-axis dimensions. Thus, as will be appreciated, each point represents an inconspicuous location where one of the reference surfaces intersects either the pressure surface fillet 63 or the suction surface fillet 65. As can be appreciated, given this configuration, the Z values given in Tables I and II represent the position of the reference plane on the Z axis. The X values given in Tables I and II represent the distance in the applicable reference plane at which a given point exists from the X axis. The Y values given in Tables I and II represent the distance in the applicable reference plane where the given point exists from the Y axis.

The various points defined by the values in Table I and Table II are connected, in whole or in part, by smooth curves or the like to define the surface configuration or contour of an exemplary fillet according to an embodiment of the present invention. be able to. Such a surface configuration or contour of the fillet may be referred to herein as a “fillet profile”. It should also be understood that the values for determining the fillet profile of fillet 50 shown in Table I and Table II are for nominal fillets. Thus, as determined from Tables I and II, the typical manufacturing tolerance of ±, including any coating thickness, is additive to the fillet surface. Thus, according to an exemplary embodiment, a distance of ± 0.05 inch in a direction perpendicular to any surface position described in Table I and Table II is a fillet profile envelope according to the fillet 50, ie, the above table. Define the range of variation between the ideal configuration of the present fillet 50 as given by I and II, and the range of variation of the fillet 50 configuration at nominal low or room temperature. Furthermore, although Table I and Table II use a specific number of points to define the surface profile of fillet 50, any number of X, Y, Z positions may be used to define this profile. Please understand that. Thus, the fillet profile defined by the values in Table I and Table II is an intermediate fillet profile for a given X, Y, Z position, and fewer X, Y, Z positions than those contained in Table I and Table II. Including those defined using Furthermore, the fillet 50 defined in Table I and Table II can be proportionally enlarged or reduced for use in the same manner as various sized tip shrouded airfoils, such an alternative implementation. It will be appreciated that the form is within the scope of the invention.

Furthermore, the present invention includes alternative embodiments of the fillet 50 that are defined in a different manner, ie other than using the points in Table I and Table II. For example, the fillet 50 extends between the leading edge 52 and the trailing edge 54 and may be described according to the path or shape of the intersection line 58. As will be appreciated, the shape of this path can be described with reference to a characteristic that will be referred to herein as “fillet height”. As used herein, the fillet height is the distance that the fillet 50 extends from the outer radial tip of the airfoil 46 toward the platform 40. More specifically, the fillet height is the distance that occurs between the intersection line 58 and the outer radial tip of the airfoil 46.

  For example, referring again to FIG. 4, it will be appreciated that at the pressure surface 53 of the airfoil 46, the height of the fillet 50 varies significantly between the leading edge 52 and the trailing edge 54. According to an exemplary embodiment, a particular way in which the height of the fillet 50 varies across the width 62 of the airfoil 46 includes five reference portions defined across the airfoil 46 for this purpose. Or it can be described in terms of specific height characteristics that occur within the range. (As explained above, the width 62 of the airfoil 46 is the distance across the chord of the airfoil 46, in other words, the distance between the leading edge 52 and the trailing edge 54 of the airfoil 46. .) As will be appreciated, these reference ranges are defined in FIG. 4 by a reference dashed line, a boundary surface, or “boundary 80”. Specifically, the five reference ranges divide the width 62 of the airfoil 46 into adjacent non-overlapping parallel portions, which for purposes of explanation are referred to herein as a front region 81, a front portion, and These are referred to as transition range 82, intermediate range 83, rear transition range 84, and rear range 85. As shown in FIG. 4, the front region 81 is a reference portion defined adjacent to the leading edge 52 of the airfoil 46. The intermediate range 83 is a reference portion that occurs at a substantially central portion of the airfoil 46. The front transition range 82 is a reference portion located between the front range 81 and the intermediate range 83. In the case of the rear region 85, it is a reference portion defined adjacent to the trailing edge 54 of the airfoil 46, while the rear transition region 84 is a reference portion located between the intermediate region 83 and the rear region 85. is there.

  The reference ranges 81, 82, 83, 84, 85 described above can be specifically located on the airfoil 46 by defining the position of the boundary 80, while defining the position of the boundary 80 with respect to the Z axis. Can do. Specifically, the boundary 80 is defined with respect to a position on the Z axis where a plane perpendicular to the Z axis can intersect the airfoil 46 at the position of the boundary 80. For purposes of this specification, these positions on the Z-axis are expressed relative to the overall chord length (ie, the length of the Z-axis between the leading edge 52 and the trailing edge 54), and thus , Given as a percentage of chord length. Specifically, the position of the leading edge 52 is given a value of 0% of the chord length, while the trailing edge 54 is given a value of 100% of the chord length. In view of this, according to a preferred embodiment, the boundary 80 separating the front region 81 and the front transition region 82 is located between 13% and 23% of the chord length. The boundary 80 that separates the front transition range 82 and the intermediate range 83 is located between 27% and 37% of the chord length. The boundary 80 that separates the intermediate range 83 and the rear transition range 84 is located between 67% and 77% of the chord length. And finally, the boundary 80 that separates the rear transition range 84 and the rear range 85 is located between 87% and 97% of the chord length.

  According to a preferred embodiment of the invention, the fillet height is given to the pressure face fillet 63 within the reference ranges 81, 82, 83, 84, 85, which reference ranges are defined above. Further, as mentioned, the fillet height is expressed in relation to the overall size of the airfoil, for example in relation to the height 61 of the airfoil 46. (As already mentioned, the height 61 of the airfoil 46 is the distance between the inner surface 60 of the tip shroud 48 and the surface of the platform 40, which is due to the tip shroud's inclination. 46). More specifically, the fillet height is expressed as a percentage of the airfoil height 61, and the position of the tip shroud 48 at the level of the inner surface 60 is that of the airfoil height 61. A position at the level of the platform 40 is considered to have a height of 100% of the airfoil height 61, while having a height of 0%. According to an exemplary embodiment of the present invention, the fillet height in the front region 81 is maintained between 3% and 13% of the airfoil height 61. The fillet height in the intermediate range 83 is maintained between 17% and 27% of the airfoil height 61. The fillet height within the rear range is maintained at 3% to 13% of the airfoil height 61. With respect to the transition ranges 82, 84, the front transition range 82 has a fillet height that smoothly transitions between the fillet height of the front range 81 and the fillet height of the intermediate range 83, while the rear transition range 84 is The fillet height smoothly transitions between the fillet height in the intermediate range 83 and the fillet height in the rear range 85.

  A tip shroud fillet according to any of the embodiments described herein provides improved support for the tip shroud, thereby extending component life and simultaneously aerodynamic flow of hot combustion gases through the turbine. Facilitate. As noted above, in terms of engine performance, it is desirable to have a relatively large tip shroud that extends over substantially the entire radially outer end of the airfoil. However, it is also desirable that the fillets remain small and streamlined for aerodynamic efficiency. Fillets according to the present disclosure effectively balance these and other competing goals so that one or more important performance goals are improved or optimized. That is, the fillet shape of the present disclosure provides a profile that effectively guides the hot gas flow through the turbine while supporting a tip shroud that is sufficiently large to prevent leakage sufficiently. Furthermore, compared to conventional fillet shapes that support similar sized tip shrouds, the fillet of the present invention reduces mechanical stress and distributes the load evenly between the pressure and suction surfaces, thereby Significantly extend the useful life of parts. The effectiveness of this fillet shape has been verified by computational fluid dynamic analysis, traditional fluid dynamic analysis, Euler and Navier-Stokes equations, flow tests, other conventional tests, and / or combinations thereof.

  As will be appreciated by those skilled in the art, many of the various features and configurations described above with respect to some exemplary embodiments are more selective to form other possible embodiments of the invention. Can be applied to. For the sake of brevity and in view of the ability of those skilled in the art, each possible repetition will not be presented or described in detail, but all combinations and Possible embodiments are intended to be part of this application. Furthermore, from the above description of several exemplary embodiments of the invention, those skilled in the art will perceive improvements, changes, and modifications. Also, such improvements, changes and modifications within the skill of the art are intended to be included within the scope of the appended claims. Furthermore, the foregoing description relates only to the described embodiments of the present application, and will be described in detail herein without departing from the spirit and scope of the present application as defined by the following claims and their equivalents. It is clear that changes and modifications can be made.

12 gas turbine engine 15 compressor 16 combustor 20 hot gas path 22 turbine 23 central axis 24 nozzle 26 rotor blade 27 rotor disk 36 arrow 40 platform 42 shank 44 dovetail 46 airfoil 48 tip shroud 49 tip 50 fillet 52 leading edge 53 Positive pressure surface 54 Trailing edge 55 Negative pressure surface 56 Seal rail 57 Cutter tooth 58 Crossing line 59 Crossing line 60 Inner surface 61 Airfoil height 62 Airfoil width 63 Positive pressure surface fillet 64 Outer surface 65 Negative pressure surface fillet 71 Reference line 72 Origin 80 Boundary 81 Front range, Reference range 82 Front transition range, Reference range 83 Intermediate range, Reference range 84 Rear transition range, Reference range 85 Rear range, Reference range

Claims (21)

An airfoil portion (46) defined between a concave pressure surface (53) and a convex suction surface (55) opposed in the lateral direction, the pressure surface (53) and the suction surface (55). An airfoil (46) extending between the leading edge (52) and the trailing edge (54) facing each other and between the tip (49) and the inner edge;
A tip shroud (48) attached to the outer tip (49) of the airfoil (46), wherein the tip shroud (48) is a planar component with an inner surface (60) facing the outer surface (64). A tip shroud (48) comprising:
A fillet (50) formed around the intersection of the airfoil tip (49) and the tip shroud (48), the fillet (50) comprising the tip shroud (48) and the airfoil portion. A fillet (50) defining a variable fillet profile around the intersection to structurally connect to (46) and to promote aerodynamic air flow around the intersection;
A turbine rotor blade for a gas turbine comprising the fillet (50),
A pressure surface fillet (63) formed between the pressure surface (53) of the airfoil (46) and the inner surface (60) of the tip shroud (48);
A suction surface fillet (65) formed between the suction surface (55) of the airfoil (46) and the inner surface (60) of the tip shroud (48);
With
As shown in Table I, the pressure face fillet (63) includes a pressure face fillet profile that substantially coincides with a point in the first set of points of X, Y, Z coordinate values in a Cartesian coordinate system. , X, Y, Z are distances from the origin in inches, and when the points in the first set of points are connected by a smooth continuous arc, the points in the first set of points Defines the pressure face fillet profile of the pressure face fillet (63);
The first set of points includes each point included between points 1 and 50 of each reference plane included between the reference plane H and the reference plane W, as shown in Table I.
Rotor blade.   The pressure surface fillet profile is within a pressure surface fillet profile envelope, and the pressure surface fillet profile envelope is at a distance of ± 0.05 inches in a direction perpendicular to the pressure surface fillet profile. Rotor blades.   The X, Y, Z coordinate values listed in Table I can be scaled as a function of the same number to provide an expanded or reduced pressure side fillet profile, the same number being a fraction, decimal, integer, The turbine rotor blade according to claim 1, wherein the turbine rotor blade is configured of any one of a mixed number and a mixed number. The tip shroud (48) further comprises first and second seal rails (56) extending circumferentially;
The inner end of the airfoil (46) is defined by a platform (40) attached to a root configured to couple the rotor blade to a rotor disk (27);
The turbine rotor blade according to claim 1.   The rotor blade according to claim 1, wherein the Z axis of the Cartesian coordinate system is oriented along a chord of the airfoil portion of the rotor blade.   The first set of points includes each point included between each point 1 and point 50 of the reference surface included between the reference surface E and the reference surface Y, as shown in Table I. The rotor blade according to claim 1.   The first set of points includes each point included between each point 1 and point 50 of the reference plane included between the reference plane A and the reference plane Z, as shown in Table I. The rotor blade according to claim 1. An airfoil portion (46) defined between a concave pressure surface (53) and a convex suction surface (55) opposed in the lateral direction, the pressure surface (53) and the suction surface (55). An airfoil (46) extending between the leading edge (52) and the trailing edge (54) facing each other and between the tip (49) and the inner edge;
A tip shroud (48) attached to the outer tip (49) of the airfoil (46), wherein the tip shroud (48) is a planar component with an inner surface (60) facing the outer surface (64). A tip shroud (48) comprising:
A fillet (50) formed around the intersection of the airfoil tip (49) and the tip shroud (48), the fillet (50) comprising the tip shroud (48) and the airfoil portion. A fillet (50) defining a variable fillet profile around the intersection to structurally connect to (46) and to promote aerodynamic air flow around the intersection;
A turbine rotor blade for a gas turbine comprising the fillet (50),
A pressure surface fillet (63) formed between the pressure surface (53) of the airfoil (46) and the inner surface (60) of the tip shroud (48);
A suction surface fillet (65) formed between the suction surface (55) of the airfoil (46) and the inner surface (60) of the tip shroud (48);
With
As shown in Table II, the suction side fillet (65) includes a suction side fillet profile that substantially coincides with a point in the first set of points of X, Y, Z coordinate values in a Cartesian coordinate system. , X, Y, Z are distances from the origin in inches, and when the points in the first set of points are connected by a smooth continuous arc, the points in the first set of points Defines the suction side fillet profile of the suction side fillet (65);
The first set of points includes each point included between point 1 and point 50 of each reference plane included between reference plane H and reference plane W, as shown in Table II.
Rotor blade.   9. The suction surface fillet profile is within a suction surface fillet profile envelope, and the suction surface fillet profile envelope is at a distance of ± 0.05 inches in a direction perpendicular to the suction surface fillet profile. Rotor blades.   The X, Y, Z coordinate values listed in Table I can be scaled as a function of the same number to provide a scaled suction surface fillet profile, the same number being a fraction, a decimal, an integer, The turbine rotor blade according to claim 8, wherein the turbine rotor blade is configured by any one of an integer and a mixed number. The tip shroud (48) further comprises first and second seal rails (56) extending circumferentially;
The inner end of the airfoil (46) is defined by a platform (40) attached to a root configured to couple the rotor blade to a rotor disk (27);
The turbine rotor blade according to claim 8.   The rotor blade according to claim 8, wherein the Z axis of the Cartesian coordinate system is oriented along a chord of the airfoil portion of the rotor blade.   The first set of points includes each point included between each point 1 and 50 of the reference surface included between the reference surface E and the reference surface Y, as shown in Table II. The rotor blade according to claim 8.   The first set of points includes each point included between each point 1 and 50 of the reference surface included between the reference surface A and the reference surface Z, as shown in Table II. The rotor blade according to claim 8. An airfoil portion (46) defined between a concave pressure surface (53) and a convex suction surface (55) opposed in the lateral direction, the pressure surface (53) and the suction surface (55). An airfoil (46) extending between the leading edge (52) and the trailing edge (54) facing each other and between the tip (49) and the inner edge;
A tip shroud (48) attached to the outer tip (49) of the airfoil (46), wherein the tip shroud (48) is a planar component with an inner surface (60) facing the outer surface (64). A tip shroud (48) comprising:
A fillet (50) formed around the intersection of the airfoil tip (49) and the tip shroud (48), the fillet (50) comprising the tip shroud (48) and the airfoil portion. A fillet (50) defining a variable fillet profile around the intersection to structurally connect to (46) and to promote aerodynamic air flow around the intersection;
A turbine rotor blade for a gas turbine comprising the fillet (50),
A pressure surface fillet (63) formed between the pressure surface (53) of the airfoil (46) and the inner surface (60) of the tip shroud (48);
A suction surface fillet (65) formed between the suction surface (55) of the airfoil (46) and the inner surface (60) of the tip shroud (48);
With
As shown in Table I, the pressure face fillet (63) includes a pressure face fillet profile that substantially coincides with a point in the first set of points of X, Y, Z coordinate values in a Cartesian coordinate system. , X, Y, Z are distances from the origin in inches, and when the points in the first set of points are connected by a smooth continuous arc, the points in the first set of points Defines the pressure face fillet profile of the pressure face fillet (63);
As shown in Table II, the suction side fillet (65) includes a suction side fillet profile that substantially coincides with a point in the second set of X, Y, Z coordinate values in the Cartesian coordinate system. , X, Y, Z are distances from the origin in inches, and when the points in the second set of points are connected by a smooth continuous arc, the points in the second set of points Defines the suction side fillet profile of the suction side fillet (65);
The first set of points includes each point included between point 1 and point 50 of each reference plane included between reference plane H and reference plane W, as shown in Table I.
The second set of points includes each point included between point 1 and point 50 of each reference surface included between reference surface H and reference surface W, as shown in Table II.
Rotor blade. The pressure surface fillet profile is within a pressure surface fillet profile envelope, the pressure surface fillet profile envelope is at a distance of ± 0.05 inches in a direction perpendicular to the pressure surface fillet profile;
The suction side fillet profile is within a suction side fillet profile envelope, and the suction side fillet profile envelope is at a distance of ± 0.05 inches in a direction perpendicular to the suction side fillet profile;
The rotor blade according to claim 15.   The X, Y, Z coordinate values listed in Table I and Table II can be scaled as a function of the same number to provide an enlarged or reduced pressure side fillet profile and suction side fillet profile, respectively, The turbine rotor blade of claim 15, wherein the same number is comprised of any one of a fraction, a decimal, an integer, and a mixed number. The tip shroud (48) further comprises first and second seal rails (56) extending circumferentially;
The inner end of the airfoil (46) is defined by a platform (40) attached to a root configured to couple the rotor blade to a rotor disk (27);
The Z axis of the Cartesian coordinate system is oriented along the chord of the airfoil (46) of the rotor blade,
The turbine rotor blade according to claim 15. The first set of points includes each point included between points 1 and 50 of each of the reference planes included between the reference plane E and the reference plane Y as shown in Table I;
The second set of points includes each point included between each point 1 and point 50 of the reference plane included between the reference plane E and the reference plane Y, as shown in Table II.
The turbine rotor blade according to claim 15. The first set of points includes each point included between points 1 and 50 of each of the reference planes included between reference plane A and reference plane Z as shown in Table I;
The second set of points includes each point included between points 1 and 50 of each of the reference planes included between reference plane A and reference plane Z, as shown in Table II.
The turbine rotor blade according to claim 15. An airfoil portion (46) defined between a concave pressure surface (53) and a convex suction surface (55) opposed in the lateral direction, the pressure surface (53) and the suction surface (55). An airfoil (46) extending between the leading edge (52) and the trailing edge (54) facing each other and between the tip (49) and the inner edge;
A tip shroud (48) attached to the outer tip (49) of the airfoil (46), wherein the tip shroud (48) is a planar component with an inner surface (60) facing the outer surface (64). A tip shroud (48) comprising:
A fillet (50) formed around the intersection of the airfoil tip (49) and the tip shroud (48), the fillet (50) comprising the tip shroud (48) and the airfoil portion. (46) to connect structurally and to promote aerodynamic airflow around the intersection, a variable fillet profile is defined around the intersection, the fillet (50) A fillet (50) including a pressure surface fillet (63) formed between the pressure surface (53) of the profile (46) and the inner surface (60) of the tip shroud (48);
A rotor blade for a turbine of a gas turbine, comprising:
A reference interface formed perpendicular to the chord of the airfoil (46) moves the airfoil (46) from the leading edge (52) of the airfoil (46) to the trailing edge (54). ) In order, including a front range (81), a front transition range (82), an intermediate range (83), a rear transition range (84), and a rear range (85), non-overlapping substantially parallel adjacencies Divided into reference ranges (81, 82, 83, 84, 85)
The reference interface dividing the front range (81) and the front transition range (82) is located between 13% and 23% of the chord length;
The reference interface dividing the front transition range (82) and the intermediate range (83) is disposed between 27% and 37% of the chord length;
The reference interface that divides the intermediate range (83) and the rear transition range (84) is disposed between 67% to 77% of the chord length,
The reference interface dividing the rear transition range (84) and the rear range (85) is located between 87% and 97% of the chord length;
The fillet height includes the height of the pressure side fillet (63) as a percentage of the total height of the airfoil,
In the positive pressure surface fillet,
The fillet height in the front region (81) is between 3% and 13% of the total height of the airfoil,
The fillet height in the intermediate range (83) is between 17% and 27% of the total height of the airfoil,
The fillet height in the rear region (85) is between 3% and 13% of the total height of the airfoil,
The fillet height within the front transition range (82) smoothly transitions between the fillet height of the front range (81) and the fillet height of the intermediate range (83),
The fillet height in the rear transition range (84) smoothly transitions between the fillet height of the intermediate range (83) and the fillet height of the rear range (85).
Rotor blade.